S3025 9.38% (s3025-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 100,000 Max Cl/Cd: 58.69 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3025-il-100000-n5.txt Download as CSV file: xf-s3025-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3025 9.38%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3366 0.09121 0.08648 -0.0339 1.0000 0.0503
-7.750 -0.3393 0.08848 0.08383 -0.0340 1.0000 0.0504
-7.500 -0.3444 0.08588 0.08133 -0.0338 1.0000 0.0501
-7.250 -0.3534 0.08346 0.07902 -0.0330 1.0000 0.0498
-7.000 -0.3606 0.08081 0.07648 -0.0329 1.0000 0.0493
-6.750 -0.3684 0.07783 0.07359 -0.0333 1.0000 0.0483
-6.250 -0.3532 0.06174 0.05731 -0.0487 0.9901 0.0245
-6.000 -0.3269 0.05645 0.05189 -0.0549 0.9816 0.0237
-5.750 -0.2976 0.05022 0.04541 -0.0618 0.9731 0.0228
-5.500 -0.2705 0.04419 0.03902 -0.0668 0.9626 0.0218
-5.250 -0.2418 0.03866 0.03301 -0.0708 0.9532 0.0218
-5.000 -0.2092 0.03422 0.02799 -0.0741 0.9459 0.0228
-4.750 -0.1802 0.03070 0.02385 -0.0756 0.9363 0.0234
-4.500 -0.1462 0.02752 0.02006 -0.0774 0.9298 0.0236
-4.250 -0.1164 0.02513 0.01718 -0.0779 0.9204 0.0238
-4.000 -0.0842 0.02308 0.01468 -0.0786 0.9124 0.0242
-3.750 -0.0513 0.02141 0.01267 -0.0792 0.9045 0.0249
-3.500 -0.0213 0.01997 0.01109 -0.0796 0.8954 0.0260
-3.250 0.0122 0.01896 0.00998 -0.0806 0.8881 0.0290
-3.000 0.0411 0.01812 0.00900 -0.0806 0.8775 0.0332
-2.750 0.0712 0.01724 0.00804 -0.0809 0.8683 0.0379
-2.500 0.1024 0.01639 0.00708 -0.0812 0.8595 0.0488
-2.250 0.1297 0.01546 0.00645 -0.0811 0.8488 0.1134
-2.000 0.1563 0.01437 0.00622 -0.0813 0.8392 0.3093
-1.750 0.1834 0.01361 0.00597 -0.0811 0.8300 0.4808
-1.500 0.2043 0.01287 0.00589 -0.0789 0.8193 0.6896
-1.250 0.2668 0.01225 0.00551 -0.0843 0.8130 0.9780
-1.000 0.3016 0.01226 0.00524 -0.0856 0.8023 1.0000
-0.750 0.3274 0.01233 0.00508 -0.0851 0.7912 1.0000
-0.500 0.3538 0.01241 0.00494 -0.0847 0.7809 1.0000
-0.250 0.3805 0.01248 0.00482 -0.0843 0.7710 1.0000
0.000 0.4056 0.01259 0.00477 -0.0836 0.7598 1.0000
0.250 0.4314 0.01271 0.00473 -0.0831 0.7493 1.0000
0.500 0.4577 0.01281 0.00468 -0.0826 0.7394 1.0000
0.750 0.4833 0.01294 0.00468 -0.0821 0.7286 1.0000
1.000 0.5087 0.01308 0.00472 -0.0815 0.7176 1.0000
1.250 0.5345 0.01321 0.00475 -0.0809 0.7071 1.0000
1.500 0.5607 0.01334 0.00476 -0.0804 0.6971 1.0000
1.750 0.5857 0.01349 0.00487 -0.0798 0.6854 1.0000
2.000 0.6110 0.01365 0.00496 -0.0792 0.6741 1.0000
2.250 0.6366 0.01380 0.00506 -0.0786 0.6631 1.0000
2.500 0.6624 0.01395 0.00516 -0.0780 0.6521 1.0000
2.750 0.6875 0.01412 0.00529 -0.0774 0.6402 1.0000
3.000 0.7125 0.01430 0.00545 -0.0768 0.6280 1.0000
3.250 0.7376 0.01447 0.00562 -0.0762 0.6158 1.0000
3.500 0.7627 0.01465 0.00581 -0.0755 0.6035 1.0000
3.750 0.7877 0.01484 0.00599 -0.0749 0.5908 1.0000
4.000 0.8125 0.01503 0.00617 -0.0742 0.5776 1.0000
4.250 0.8371 0.01523 0.00638 -0.0735 0.5637 1.0000
4.500 0.8615 0.01544 0.00663 -0.0728 0.5490 1.0000
4.750 0.8855 0.01566 0.00688 -0.0720 0.5333 1.0000
5.000 0.9093 0.01590 0.00715 -0.0712 0.5167 1.0000
5.250 0.9328 0.01615 0.00745 -0.0703 0.4993 1.0000
5.500 0.9560 0.01643 0.00773 -0.0694 0.4812 1.0000
5.750 0.9789 0.01673 0.00805 -0.0684 0.4622 1.0000
6.000 1.0012 0.01706 0.00842 -0.0675 0.4420 1.0000
6.250 1.0231 0.01744 0.00881 -0.0664 0.4217 1.0000
6.500 1.0445 0.01785 0.00925 -0.0653 0.3994 1.0000
6.750 1.0652 0.01831 0.00971 -0.0641 0.3773 1.0000
7.000 1.0853 0.01881 0.01023 -0.0629 0.3540 1.0000
7.250 1.1048 0.01937 0.01078 -0.0615 0.3315 1.0000
7.500 1.1235 0.01999 0.01143 -0.0602 0.3089 1.0000
7.750 1.1418 0.02064 0.01210 -0.0588 0.2869 1.0000
8.000 1.1589 0.02137 0.01282 -0.0572 0.2651 1.0000
8.250 1.1756 0.02211 0.01360 -0.0557 0.2431 1.0000
8.500 1.1900 0.02297 0.01443 -0.0539 0.2188 1.0000
8.750 1.2028 0.02391 0.01534 -0.0520 0.1925 1.0000
9.000 1.2141 0.02495 0.01629 -0.0500 0.1643 1.0000
9.250 1.2239 0.02609 0.01734 -0.0479 0.1373 1.0000
9.500 1.2314 0.02730 0.01845 -0.0456 0.1138 1.0000
9.750 1.2389 0.02852 0.01965 -0.0432 0.0930 1.0000
10.000 1.2443 0.02994 0.02103 -0.0407 0.0761 1.0000
10.250 1.2481 0.03154 0.02263 -0.0383 0.0591 1.0000
10.500 1.2489 0.03343 0.02451 -0.0358 0.0468 1.0000
10.750 1.2482 0.03553 0.02668 -0.0335 0.0386 1.0000
11.000 1.2459 0.03786 0.02901 -0.0316 0.0342 1.0000
11.250 1.2467 0.04003 0.03137 -0.0300 0.0309 1.0000
11.500 1.2458 0.04247 0.03395 -0.0288 0.0287 1.0000
11.750 1.2419 0.04534 0.03691 -0.0278 0.0269 1.0000
12.000 1.2376 0.04838 0.04008 -0.0271 0.0260 1.0000
12.250 1.2358 0.05135 0.04325 -0.0266 0.0251 1.0000
12.500 1.2333 0.05448 0.04657 -0.0263 0.0242 1.0000
12.750 1.2309 0.05773 0.05000 -0.0261 0.0235 1.0000
13.000 1.2285 0.06108 0.05351 -0.0262 0.0230 1.0000
13.250 1.2261 0.06453 0.05712 -0.0264 0.0224 1.0000
13.500 1.2237 0.06808 0.06082 -0.0267 0.0219 1.0000
13.750 1.2210 0.07176 0.06467 -0.0272 0.0214 1.0000
14.000 1.2183 0.07553 0.06858 -0.0278 0.0210 1.0000
14.250 1.2148 0.07952 0.07268 -0.0287 0.0205 1.0000
14.500 1.2106 0.08367 0.07694 -0.0296 0.0199 1.0000
14.750 1.2060 0.08819 0.08166 -0.0310 0.0196 1.0000
15.000 1.2004 0.09306 0.08676 -0.0327 0.0193 1.0000
15.250 1.1927 0.09844 0.09238 -0.0350 0.0190 1.0000
15.500 1.1835 0.10428 0.09844 -0.0376 0.0187 1.0000
15.750 1.1728 0.11066 0.10504 -0.0409 0.0185 1.0000
16.000 1.1613 0.11747 0.11206 -0.0445 0.0184 1.0000
16.250 1.1479 0.12500 0.11979 -0.0488 0.0183 1.0000
16.500 1.1333 0.13317 0.12815 -0.0537 0.0184 1.0000
16.750 1.1167 0.14231 0.13746 -0.0593 0.0185 1.0000
17.000 1.0984 0.15245 0.14776 -0.0656 0.0188 1.0000
17.250 1.0788 0.16371 0.15914 -0.0726 0.0191 1.0000
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Polar data table (+)
Polar graphs
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